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The topic is so large, and life is so short
Old fashioned rotating iron gyroscopes only

Other types include
- Fibre optic gyroscope
- MEMS gyroscopes, a subset of Vibrating structure gyroscope

as of August 6, 2021

Most of us have been fascinated,
at least for a minute,
by a child's "top" and/or a gyroscope.

Table of Contents
     - Introduction
     - My experience
     - "my" defunct 1952 rate gyro & a working purchase
     - Vtg Aircraft Part SPERRY Directional GYRO Indicator TYPE C-5 Aviation gyroscope
     - Humphreq Vertical Gyroscope Aircraft Helicoptor VM02-0110-1
     - Interesting On-Line Manuals
     - Saturn Guidance .doc - from Charles Carter
     - Temporary Other - Feb 2018
     - Minuteman ICBM guidance unit
     - Apollo IRIG Gyroscope, by CuriousMarc
     - The A4 / V2 rocket in detail: Bringing a V2 rocket gyro back to life - YouTube
     - Gyros & Stuff from Brooke Clarke < brooke @ pacific . net > Jul 23, 2019
     - Commercial Usage - Jan 7, 2020
     - Walter Lewin, Lect 24, Gyroscopes, VERY NON-INTUITIVE

When the rotor isn't spinning, a gyro is just a floppy thing,
but when the rotor is spinning, the dynamics are so unusual !!
Odd that just making the rotor spin causes such a difference !!

" 8.01x - Lect 24 - Rolling Motion, Gyroscopes, VERY NON-INTUITIVE", by Walter Lewin of MIT
Great demo props, Gyro starts at minute 14, for 35 minutes

My experience - not much :-((
In the Army, I was in the Nike antiaircraft missile program which used free and rate gyros as part of the missile guidance control system. However, I was in the radar/guidance area, not the missile area - so never physically saw the gyros.

After the Army, I considered myself a real techie hot shot, and lucky enough got a job at Minneapolis Honeywell Aero Division testing "HIG" and rate gyros. I can wave my hands and kind of explain how those work,
but a gyro

- configured as a compass,
- capable of finding "True North" using the rotation of the earth and "down"
- used for navigation,
eluded me.

A friend is an ex-submarine electronic tech who was inpart responsible for maintaining a gyro compass,

and another friend (Norman Paik) made his bundle selling Litton gyrocompasses.
Litton LN-3 Inertial Navigation System of an F-104 Starfighter

The purpose of this page is to wave my hands some more

and imagine that I understand the operation of gyro compasses such as used in ships, especially submarines :-))

A bit of a confusion - an aircraft "gyro compass" is frequently a free gyro which must be frequently preset to magnetic north. It is used to indicate "North" during turns and accelerations that cause magnetic compasses trouble. It is not self-aligning (using the earth's rotation) with true north in the sense of a marine gyro compass.

When stabilised the spin axis is maintained in the meridian plane by a precession equal but opposite to the drift at the particular latitude. When there is no tilting effect the marine gyrocompass will lose its directional properties and become useless. This is the case at the poles and also when a vehicle moves due west with a speed equal to the surface speed of the Earth. Because the latter condition can easily exist in an aircraft in the middle and upper latitudes, it cannot be used for air navigation.

Pictures of the SperryRand MK-19 gyro compass installation in the Nautilis Submarine on exhibit at Groton, CT.



"my" defunct 1952 rate gyro & a working purchase
- started December 2018, updated February 26, 2019.
Norman Paik was an army friend and was later associated with Litton Gyroscope. He died in December 2018. His widow, Kathleen, had heard Norman and I talking gyroscopes.
She asked if I wanted a souvenir Honeywell Rate Gyro Norman had, and set it to me :-) She had warned me that the souvenir probably had a defective motor winding.
And it did (as measured with an ohmmeter) :-( However, something is better than nothing, and here it is - fresh out of the mailed box.
Later correction, scraping the pins hard with "alligator clips" yielded the resistance almost identical to the purchased gyro, and 400 Hz will spin the gyro :-))
On Feb 22, 2019, Marc Verdiell showed me the clean up job he had performed on this dusty corroded gyro. Looks almost new - even the spring looks metallic :-))
  The right hand pictures are of a similar second hand rate gyro I purchased in January 2019 from E-Bay "Flying Fish Aircraft Parts" - Collins Honeywell 3326-2 Rate Gyro Assembly JG7005A55 GUARANTEED WORKING (8783)
On Feb 26, Marc Verdiell e-mailed:
"I received the [400 Hz] inverter yesterday. Today I could wait no more. Both of your gyro have been spun... I did not spin the “Hawaiian” one to full speed, but it spun quite well too.
Both are quite noisy, so I am a bit worried about the state of the bearings / balancing. I spun it first with cover on, just in case. I spun it down right after it seemed to have reached steady state.
Towards the end of the video I rotate it a bit and it does its gyro rate thing faithfully.
Takes about 50W to spin up, gets down to less than half that at speed.

New YouTube of spin up and spin down

So, what do we have here??
This is the under side of the base plate
Unfortunately, the specifications are not available (on-line)
There is no rating, such as input power, max measurable rate
I *guess* the measurable rate might be 30 degrees/second, a common rating when I was testing aircraft rate gyros

This shows important gyro axes (the plural of axis)
  • Spin Axis - the axis of the spinning mass
  • Force or Sense Axis - rate of rotation about this axis is what this instrument measures
  • Precession Axis - Rotation about the Sense Axis, above, applies force about this axis. This force is countered by the rusty Centering Spring
Sense Potentiometer - very fine wires wound about an insulating rod.
  • a positive voltage is applied to one end, see silver solder
  • a negative voltage is applied to the other end
  • the two pick-off brushes (actually wires) pick off positional voltage (rotation about the precession axis) for output
The Brits in The A4 / V2 rocket in detail: Bringing a V2 rocket gyro back to life (minute 6:29) refer to these tiny "brushes" as "fly legs".

A better view of the connection to the outside world.
pins A & B connect to the spin motor (DC resistance 75 ohms)
Pin E connects to the top of the Sense Potentiometer (512 ohms)
Pin F connects to the bottom of the Sense Potentiometer
Pin G connects to the pick-off brush of potentiommeter
Amphenol 7 Pin Female Plug MS3106A 16S-01S, MIL SPEC - works fine
Three Rotational Power Contact Points for the gyro motor
co-axial with the Precession Axis.
The other side of the Rate Gyro.
Seen is a corroded cylindrical capacitor. I'm *guessing* that it is used to phase shift the gyro power (likely single phase 110 volts AC 400 Hz). This can provide starting torque for the gyro (spin motor) - the third wire into the gyro motor. Since this capacitor is not polarized, and low loss, no need to disconnect it after start-up.
The side opposite to the electrical plug.
The right hand structure is another view of the Sense Potentiometer
And of course a top view :-)
Unknown structure, may be an off null switch?
The two wire contacts ('brushes") may be positioned between two conductive plates. This may be a switch to indicate some finite rotation about the sense axis of the gyro?

Vtg Aircraft Part SPERRY Directional GYRO Indicator TYPE C-5 Aviation gyroscope
AirForce type C-1, C-5, (Sperry) Handbook, Operation, Service, Overhaul Thanks to Marc Verdiell

Marc purchased a nice, variable frequency, 3-phase 115 volt output power supply, and spun this unit up July 16th, 2021 - Initial Report
- and the C-5 doing its thing on Marc's rate table (1.5 min)

Humphreq Vertical Gyroscope Aircraft Helicoptor VM02-0110-1
Vertical Gyroscope thanks to Ken Shirriff
ad from e-bay

Interesting On-Line Manuals
Elementary Non-technical Introduction to Gyro Gompasses
Good Start A 1944 Sperry (before Rand) GYRO-COMPASS GYRO-PILOT MANUAL
Add gun stabilization A navy document MK-19 and MK-23 gyro compass. 6.5 MByte
Wonderful ;-)) THEORY OF THE GYROCOMPASS ( ) 1,2 MByte Local copy)
Directional Gyro Indicators AirForce type C-1, C-5, (Sperry)
Handbook, Operation, Service, Overhaul
Apollo reference "Apollo guidance, navigation and control - Design survey of the Apollo inertial subsystem"
"Apollo Guidance, Navigation, and Control (GNC) - NTRS - NASA"
THE collection of Apollo info
including Spec for procurement of Apollo Inertial Reference Integrating Gyro Thanks Mike Stewart

Temporary Other - Feb 2018
from "" Feb 2, 2018

please have a look to the photos.
The "golden" gyro was fully tested in 1994.
Both seem to be in good working condition.
Both have 3,4 kg and give the same noise shaking slightly...
Which one should i open ?
I think the best way will be to desolder a small part of
the thin sheet metal strip of 1 cm size around the gyro, beginning at
the thick solder point and then continue mechanically with
assisted heat and rolling the sheet metal over a kind of a can opener.
Best regards

as announced i opened the gyro.
Please have a look...
Due to the size of the data i reduced the resolution of the pictures.
If you want more details then tell me what picture you mean...
Best regards


























Minuteman ICBM guidance unit
Ignacio Menendez May 15, 2019, sent:
also see PIGA accelerometer

Apollo IRIG Gyroscope
Apollo AGC Part 9: Unboxing my Apollo IRIG Gyroscope, by CuriousMarc

Gyros & Stuff from Brooke Clarke < brooke @ pacific . net > Tue, Jul 23, 2019

Hi Ed:

While surfing things related to Apollo I came across a link to your gyro web page.
Recently I saw the movie "First Step" where, after some research, discovered the 
"Box Sextant" used to train the astronauts to find the navigation stars 
they would need to sight for the AGC.

My Gyroscope web page is at:
also see: - it never worked

I also did a lot of research on W.W.II torpedoes and discovered a major 
disconnect between the max range and their ability to hit anything.  
The max range is over 10X the range at which they can hit a target.  
Ford Inst. Co. patented the torpedo data computer and also the Gun Director 
for big guns on ships.  They both are trying to solve the same problem 
of a ballistic weapon firing from a moving platform trying to hit another 
moving platform where the time from firing to impact is quite long.  
It's my contention that torpedoes of that type, big guns that fire at 
high elevation angles and iron bombs delivered from a horizontal plane 
have never been accurate weapons.

And the information most related to your Nike stuff:

The Sidewinder missile and proximity fuse were motivated by how hard 
it was to shoot down aircraft, see:

Have Fun,

Brooke Clarke
1. The extent to which you can fix or improve something will be limited by how well you understand how it works.
2. Everybody, with no exceptions, holds false beliefs.

Commercial Usage - Jan 7, 2020
taken from, Jan 7, 2020
Inertial Measurement Units and Inertial Navigation

The Inertial Measurement Unity (IMU) is an integrated sensor package that combines multiple accelerometers and gyros to produce a three-dimensional measurement of both specific force and angular rate, with respect to an inertial reference frame, as for example the Earth-Centered Inertial (ECI) reference frame. Specific force is a measure of acceleration relative to free-fall. Subtracting the gravitational acceleration results in a measurement of actual coordinate acceleration. Angular rate is a measure of rate of rotation. It is important to note that in recent years the term IMU has become an umbrella term used to describe a wide assortment of inertial systems including Attitude Heading Reference Systems and Inertial Navigation Systems. In the context of this writing, we will use the term IMU in accordance with its classical meaning to describe the combination of only a 3-axis accelerometer combined with a 3-axis gyro. An onboard processor, memory, and temperature sensor may be included to provide a digital interface, unit conversion and to apply a sensor calibration model. The IMU by itself does not provide any kind of navigation solution (position, velocity, attitude). It only actuates as a sensor, in opposition to the INS (Inertial Navigation System), which integrate the measurements of its internal IMU to provide a navigation solution. For instance, an Inertial Navigation System (INS) uses an IMU to form a self-contained navigation system which uses measurements provided by the IMU to track the position, velocity, and orientation of an object relative to a starting point, orientation, and velocity.

History of Inertial Navigation

The field of inertial navigation is a well-established field of study and extends way before the advent of MEMS technology. The first inertial sensors were developed and tested by rocket designers such as Robert Goddard and Wernher von Braun in the early 1930s. Later inertial sensors technology was perfected by institutions such as Drapers Labs, creating the first Inertial Navigation Systems. Inertial navigation made possible many of the great spaceflight achievements such as the Apollo program.

Up until the advent of MEMS technology, inertial sensors consisted of precision mechanical gyros and accelerometers. Due to their high costs, inertial sensing technology was reserved for high-end aerospace applications. As MEMS inertial sensor technology has matured over the years low-cost solid state chip level inertial sensors have become available as alternatives to the older mechanical inertial sensors. While these new MEMS based sensors offered lower overall performance than their mechanical counterparts, they also offered drastically reduced size, power, and cost.

The Inertial Sensor Market

The inertial sensor market spans an enormous range in terms product price and performance. There are six orders of magnitude difference in price and performance between the highest end inertial systems and the lowest. This can lead to great confusion for many buyers when dealing with component selection and pricing. The goal of this guide is to provide a crash course on what is available and possible with inertial sensors.

First of all there is not agreed upon definitions of high, medium, and low-grade performance when it comes to inertial sensors. What one expert considers high end may be low end to another and vice-versa. When you are searching for inertial systems you may come across the terms Tactical grade or Automotive grade. These terms define different performance classes which similar inertial sensors can be grouped. In general, inertial sensors can be grouped into one of the following four performance categories.

  • Marine & Navigation Grade
  • Tactical Grade
  • Industrial Grade
  • Automotive & Consumer Grade
Marine & Navigation Grade

Aside from the custom inertial navigation systems used on Intercontinental ballistic missiles, the marine grade inertial systems is the highest grade sensors that are commercially available. They provide the best overall performance in terms of both determining position and orientation. These systems are typically used on ships, submarines, and some spacecraft. A high-end marine-grade INS can cost over 1 million dollars. These systems will typically provide un-aided navigation solution drifts that are less than 1.8 km per day. This means that if the device were left stationary for one day, due to slight errors in the sensors and imperfect sensor calibrations, after integrating the position solution, the calculated position after one day would be 1800 meters away from the sensors actual position. This represents the best that is possible with commercially available inertial sensing technology. Navigation grade systems have slightly lower performance than the marine systems and are typically used on commercial airliners and military aircraft worldwide. A navigation grade system will typically have less than 1.5km drift per hour. These systems cost around $100,000 and have a size of about 6in x 6in x 6in. A navigation grade system can be combined with GPS to create positioning systems that are accurate to within centimeters in real-time. An example of a navigation grade IMU is the HG9900 IMU made by Honeywell.

  Automotive & Consumer Grade

The lowest grade of inertial sensors is often referred to as automotive grade. They are typically sold as individual accelerometers or gyros, however many companies have begun to combine multiple accelerometers and gyros from different manufactures to create self-contained IMU units. This grade of IMU's are not accurate enough to be used for inertial navigation even when integrated with other navigation systems such as GPS. These sensors typically have good repeatability, and if they are calibrated after installation then they can be used as part of an industrial grade sensor, an Attitude Heading Reference System (AHRS), or a Pedestrian Dead-Reckoning System. Typically these sensors are used in anti-lock braking systems, airbags, active suspension systems, gaming controllers, and entertainment systems. The main difference between automotive grade and industrial grade lies in the quality of sensor calibration.

Which grade Inertial sensors are right for my application

Determining which type of inertial sensor is right for your application can be a difficult process due to the lack of information available pertaining to the subject. Datasheets for inertial sensors can be very confusing and make it difficult for potential buyers to compare different products. The first step is to determine which grade of sensors is required for your application. Trying to use an industrial grade IMU in an application that requires navigation grade performance will only lead to enormous levels of frustration and confusion. This is the step where you want to pick the right tool for the job. You don't want to use a bulldozer where you need a shovel, and you certainly don't want to use a shovel where you should be using a bulldozer.

In order to compare the performance of the different grade inertial sensors we will analyze them for two different use cases. Each case corresponds to a common use for inertial sensors.

Case 1 - Unaided Position Estimate

This case corresponds with using an IMU as a stand-alone inertial navigation solution without the assistance of GPS or any other external reference. Below is an overview of the typical errors for each grade of inertial sensors.

When determining how well an inertial system will perform as an inertial navigation system, a first order estimate is to assume that the errors in position will be caused only by the errors in the accelerometer bias. Errors in the position estimate will actually be caused by many factors including the gyro bias stability, accelerometer scale factor uncertainty, and many other parameters, however the largest contribution will be due to un-corrected errors in the accelerometer bias. Any bias in the accelerometer horizontal axes will cause an bias in the calculated orientation of the object in terms of pitch and roll. Since we have to subtract out gravity from the IMU accelerometer measurement prior to integration, any error in the calculated orientation will cause us to not correctly subtract out the gravity from the acceleration measurement. Since the amount of acceleration of an object is typically much smaller than the acceleration due to gravity (9.81 m/s^2), subtracting out gravity incorrectly can lead to very large errors in the estimated inertial acceleration which will directly integrate into position errors. The error in position due to a bias in the accelerometer will have quadratic growth with time.

The misalignment of the accelerometer axes will also performance of the inertial navigation system. It is important that each of the axes of the accelerometer are aligned perfectly with an orthogonal coordinate system. Errors in misalignment will propagate into position errors as shown in the table below.

The above table reinforces the importance of sensor calibration. Automotive sensors typically have package misalignments of around 1 and inter-axis misalignments of greater than 0.1. Industrial grade inertial sensors will typically have misalignments calibrated to within 0.05.

Errors due to Gyro Bias Walk and Noise

The gyro noise and bias uncertainty will affect the position estimate error of an inertial navigation system. The affect of the white noise upon the integrated orientation angle is quantified by the gyro angle random walk parameter. The parameter multiplied by the square root of the integration time gives an estimate of the 1 sigma angle walk due to the gyro white noise. For navigation grade systems this can be a predominant source of error. For tactical, industrial, and automotive grades this does have an effect, however it can have an order of magnitude less effect than an accelerometer bias error that is left unaccounted for.

How to estimate horizontal position error

You can estimate the amount of horizontal position error for a static case by simply using the accelerometer bias error given in the manufactures datasheet. For example let us look at a typical automotive grade MEMS accelerometer datasheet. The below excerpt is from the datasheet of the LIS344ALH 3-axis MEMS accelerometer made by ST Micro.

From the datasheet we find that the zero-g level is known to within 5%. Since Vdd for this part is 3V, this means we have a 75mV uncertainty. The datasheet also tells us that the sensitivity is 0.6 mV/mg. This means that the total uncertainty in the accelerometer bias is 125 mg. To calculate the maximum static case horizontal position error use the following formula:

In the above equation replace T with the time measured in seconds. For instance after 10 seconds with this accelerometer you could have as much as 60 meters error in calculated position.

The uncertainty in the accelerometer bias is the primary reason why automotive grade accelerometers cannot be used for inertial navigation. If this sensor is properly calibrated however, then the uncertainty in the accelerometer bias can be reduced by nearly two orders of magnitude, reducing the horizontal position error to within a few meters over the same 10 second period.

Errors due to axis misalignment can be calculated using the below formula.

The uncertainty due to the gyro angle random walk can be calculated as

Case 2 - Relative Orientation Determination

Inertial sensor can also be used to determine the orientation as a function of time. Without an absolute reference an IMU can only be used to track changes in orientation from some initial point in time. For absolute orientation tracking you will need to combine an IMU with an absolute reference sensor such as magnetometer, camera, or GPS. Combining an IMU with a magnetic sensor creates what is known as an Absolute Heading Reference System (AHRS). For this case we will look at the error caused by the accelerometer that influence the orientation estimate. An AHRS determines orientation by making the assumption that the measured acceleration vector minus the known inertial acceleration is equal to the gravity vector. For cases where the actual inertial acceleration is unknown the AHRS assumes that the measured acceleration on the accelerometer is the actual gravity vector. Due to this assumption any errors in the accelerometer will translate into errors in the estimated direction of the downward direction. The gyros will dampen out much of the time based disturbances in the acceleration, however any constant errors in the accelerometer calibration parameters will directly propagate into orientation errors.

Static Errors Due To Accelerometer Bias

A bias in accelerometer will affect the pitch/roll by perturbing the measured acceleration vector. This will affect the direction of the measured gravity vector, directly contributing to errors in the estimated pitch and roll. The below table shows typical errors in pitch and roll that are contributed due to the errors in accelerometer bias.

Errors in accelerometer bias for automotive grade sensors are mainly due to imprecise calibration. The errors in the industrial and tactical grade are typically due to changes in temperature which cause the accelerometer bias to deviate in ways that cannot be accounted for by the sensor calibration model. The accelerometer bias may also be subject to long-term drift that isn't accounted for in the sensor model.

Static Errors Due to Accelerometer Misalignment

Errors due to accelerometer misalignment will on a first order translate directly into errors in pitch/roll. Shown below are typical misalignment calibration accuracy for each grade inertial sensors.

Misalignments are removed by performing a tumble test during the calibration procedure.

Static Errors Due to Accelerometer Scale Factor

The errors due to scale factor of the accelerometer can also contribute to the errors in the measured orientation. The magnitude of error is dependent upon the residuals after calibration. Shown below is the typical accelerometer scale factor errors for each of the different grad IMU's.

The maximum error in pitch/roll can be analyzed by assuming that the sensor is in an orientation where the pitch and roll both equal 45. In this case a scale factor error in either axis will stretch one dimension of the vector, thus affecting the measured angle.

Dynamic Errors Due to Gyro Scale Factor

The gyro scale factor has a substantial error on the accuracy of the integration of the angular rates during dynamic motion. If the scale factor is off, then the motion tracked by the gyros will not be correctly scaled and significant errors may result after the motion is complete. As an example consider the case of picking up an IMU, rotating it around the one of its axes by 360 degrees and setting it back down. Ideally the unit should read the same orientation as it did prior to the maneuver. The table below shows some the errors for this simple maneuver for each grade sensor.

The table shows an order of magnitude difference from the navigation grade to the tactical grade, an order of magnitude from the tactical to the industrial, and two orders of magnitude from the industrial to the automotive. As you can see from the table, automotive grade sensors do not provide sufficient accuracy for neither inertial navigation nor accurate orientation tracking. Only when the automotive sensors are subjected to a thorough calibration do they provide sufficient performance to perform basic navigation techniques.

Dynamic Errors Due to Gyro Misalignment

The gyro misalignment will affect how the angular rates are measured in each of the coordinate directions. Misalignment causes distortions in the measured angular rate vector, which result in errors in resulting orientation after the angular rates are integrated. As a simple example consider the same case described above for the gyro scale factor where we rotate the IMU around a only the Z-axis by 360 degrees and return to the same orientation. If there exists misalignments in the other X and Y axes then they will inadvertently pick up angular rate from the Z-axis rotation even though no physical rotation was conducted around the X and Y axes. The table below outlines the maximum amount of error that would be recorded in pitch and roll assuming that the given amount of axis misalignment was present.

As with many of the other parameters you can see that there is clearly an order of magnitude difference in performance between each of the different grades with respect to errors due to gyro axis alignment.

Initial Sperry C-5 Spinup Report - from Marc, July 16, 2021

I got the gyro to do self-leveling! Cleaned the contacts, and I could see it switching the voltage to the coil. But it’s quite subtle – it moves very slowly. It sends a pretty low voltage to the rotor coil – a few volts only, from an auto-transformer. It’s on purpose. It engineered to compensate drift, so it’s about the same order of magnitude as the drift induced torque, just a bit more. Takes several minutes for it to get back to center if you purposely (manually by pushing on it) torque it off center. It’s still a pretty noisy beast, and it sometimes makes scary tones. I would think its bearings are pretty much done, we should probably not spin it too much more.

But I learned a lot and did not break anything. I was very impressed on how incredibly stiff against any rotation it is once it is spun up. When you try to push it around, it feels like it is bolted down solid. By pushing really hard you can torque it up or down by precession, but the base rotation is so small you will not feel it nor will you see it change its indicated angle. It’s as if it was locked in place solid. Now I understand why they spin bullets and rockets so they go straight, but I did not expect the effect to be so incredibly strong.